A fluidic oscillator device, in particular for a or in a flow control system for an aircraft or spacecraft, has a first and a second fluidic actuator, wherein each of the actuators has an inlet for supplying pressure and a first and a second outlet, from which an actuator flow can be discharged. The device further has a fluidic control for controlling an oscillating discharge of the actuator flow from the first and second outlet of the actuators, wherein the control has a connection portion which is arranged between the first actuator and the second actuator.
Aircraft or spacecraft fluidic oscillator device
12.05.2020
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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